Abstract
Abstract : Three supersonic nozzle configurations were developed and tested using the LTCC materials system. An isentropic model was generated to determine the overall size of each nozzle and the nozzle curvature was defined using a Method of Characteristics approach. Each nozzle was tested using a cold gas test stand at several pressures. The experimental thrust measurement was compared to the isentropic model and several 3D CFD models. A schlieren visualization system was created to further validate the CFD model results.. A hydrogen peroxide catalyst chamber was modeled and constructed. Four configurations were developed to determine the effect on reactor performance. The device inlet pressure and surface temperature were measured during a constant inlet mass flow rate of hydrogen peroxide propellant. The performance of the LTCC catalyst chamber and nozzle indicates that this technology can be used as a feasible micro-propulsion device.
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